2024 CQ Flashcards
Q.1.1 What does TO/GA AFDS command when engaged for takeoff?
The AFDS commands pitch attitude in the following order:
• 15° nose up after lift-off until a sufficient climb rate is acquired. Then, pitch is commanded to maintain MCP speed plus 20 kts
Reference: FRM B737NG/MAX 4.2.2
Q.1.2 What does the AFDS pitch command if an engine failure occurs at or after lift-off?
At lift-off:
• If an engine failure occurs on the ground, the pitch command target speed at lift-off is V2 or airspeed at lift-off, whichever is greater.
After lift-off:
• If an engine failure occurs, the pitch command target speed is:
- V2, if airspeed is below V2.
- Existing speed if airspeed is between V2 and V2 + 20.
- V2 + 20, if airspeed is above V2 + 20.
Reference: FRM B737NG/MAX 4.2.4.1
Q.1.3 When below 2,000 ft RA, what N1 will the A/T command with one push of either TO/GA switch?
Thrust advances toward the reduced go-around N1 to produce 1000 to 2000 fpm rate of climb.
Reference: FRM B737NG/MAX 4.2.4.3.7
Q.1.4 What N1 will the A/T command with a second push of the TO/GA switch?
The A/T advances to the full go-around N1 limit.
Reference: FRM B737NG/MAX 4.2.4.3.7
Q.1.5 During a go-around, what airspeed will be commanded after pushing either TO/GA switch?
The command airspeed cursor automatically moves to a target airspeed for the existing flap position based on maximum takeoff weight calculations.
Reference: FRM B737NG/MAX 4.2.4.3.7
Q.1.6 During a go-around, what changes in the MCP pitch mode if you engage the autopilot?
TO/GA terminates, and LVL CHG engages.
Reference: FRM B737NG 4.2.4.3.7 /MAX 4.2.4.1
Q.1.7 During Approach, how do you exit the APP (VOR/LOC & G/S captured) mode?
• Pushing a TO/GA switch
• Disengaging A/P and Turning off both F/D switches (without having one engaged)
• Retuning a VHF NAV receiver
Reference: FRM B737NG/MAX 4.2.4.3.
Q.1.8 What does white “A/T LIM” indication mean on Thrust Mode Display?
The FMC is not providing the A/T system with N1 limit values. The A/T is using a degraded N1 thrust limit from the related EEC.
Reference: Reference: FRM B737NG/MAX 4.1.8
Q.1.9 What does a flashing “8” or “A” mean on IAS/MACH window?
The overspeed “8” or underspeed “A” limiting symbol appears when the commanded speed cannot be reached.
Reference: FRM B737NG/MAX 4.1.2
Q.1.10 In which MCP pitch mode are SPD INTV and ALT INTV available?
VNAV
Reference: FRM B737NG/MAX 4.1.3
Q.1.11 To arm VNAV on the ground, what criteria must be met?
• A valid flight plan has been entered.
• Performance data has been entered and executed.
• Both flight director switches have been switched ON.
Reference: FRM B737NG 11.9.2.1, FRM B737MAX 4.1.3
Q.1.12 On the ground with the VNAV armed prior to takeoff, at what altitude does the VNAV become active?
400 ft AGL
Reference: FRM 4.1.3
Q.1.13 During a VNAV PTH descent, what speed will the FMC attempt to maintain?
A path descent uses the target speed for planning purposes only. There is no attempt to maintain the target speed during the idle portion of the descent.
Reference: FRM 11.4.6.6.4
Q.1.14 What is the importance of an amber FMC Alert light on Autopilot/Autothrottle Indicators Panel?
The light indicates an MCDU or Fuel alerting message is displayed in the MCDUs scratchpad. In the MAX, Fuel alerts will also be indicated on the Engine Display.
Reference: FRM B737NG/MAX 11.1.1.7
Q.1.15 What is the green rectangle around the pitch, roll and A/P status in the FMA?
Mode Change Highlight Symbol (green box) means the mode was engaged within the last 10 seconds.
Reference: FRM B737NG/MAX 4.1.9
Q.1.16 What is the best indication to ensure an Autopilot is engaged after selection?
FMA indicating a changeover from FD to CMD
Reference: FRM B737NG/MAX 4.1.9
Q.1.17 When in Autothrottle (A/T) Engaged Mode, what does “ARM” indicate on the FMA?
No autothrottle mode engaged. Thrust lever autothrottle servos are inhibited; the Pilot can set the thrust levers manually. Minimum speed protection provided.
Reference: FRM B737NG/MAX 4.2.2.7.1
Q.1.18 At what speed during takeoff roll does A/T mode change to “THR HLD”?
At 84 KIAS.
Reference: FRM B737NG/MAX 4.2.4.1
Q.1.19 When does automatic reduction to climb thrust occur when using the autothrottle for takeoff?
When reaching the selected thrust reduction altitude which is shown on the FMC MCDU TAKEOFF REF 2/2 page during preflight, or when the aircraft levels off in ALT HOLD or VNAV PTH
Reference: FRM B737NG/MAX 4.2.4.1
Q.2.1 During cruise, you notice a BAT DISCHARGE light illuminated. When you check the battery voltage, what would you expect to see as normal?
22-30 volts
Reference: FRM B737NG/MAX 6.2.5.2
Q.2.2 How long can a fully charged battery/batteries provide standby power?
Single Battery: 30 minutes minimum
Dual Battery: 60 minutes minimum
Reference: FRM B737NG/MAX 6.2.5.2
Q.2.3 You receive a MASTER CAUTION/ELEC and notice a DRIVE light illuminated on the overhead panel. What has occurred and what should be your next course of action?
Integrated drive generator (IDG) low oil pressure caused by one of the following:
• IDG failure
• Engine shutdown
• IDG automatic disconnect due to high oil temperature
• IDG disconnected through generator drive DISCONNECT switch
Carefully assess any related information. Reference the QRH for corrective action.
Reference: FRM B737NG/MAX 6.1.3
Q.2.4 Why does the QRH direct the generator drive DISCONNECT switch to be placed in the Disconnect position?
Disconnection reduces risk by preventing further generator drive damage.
Reference: QRH 6.1
Q.2.5 What does a SOURCE OFF light indicate?
No source has been manually selected to power the related transfer bus, or the manually selected source has been disconnected.
Reference: FRM B737NG/ MAX 6.1.4
Q.2.6 How is the transfer bus powered if the respective IDG is disconnected?
If the BUS TRANSFER switch is in the AUTO position, the source powering the opposite transfer bus automatically picks up the unpowered transfer bus through the bus tie breaker.
Reference: FRM B737NG/MAX 6.2.3
Q.2.7 While in cruise flight, you receive a MASTER CAUTION/ELEC and notice a TR UNIT light illuminated on the overhead panel. What could have caused it?
• TR1 failed; or
• TR2 and TR3 failed
Reference: FRM B737NG/MAX 6.1.2
Q.2.8 While in cruise flight, you receive a MASTER CAUTION/ELEC and the following lights on the overhead panel: TRANSFER BUS OFF (both), SOURCE OFF (both), and GEN OFF BUS (both). What provides power to essential systems immediately?
Standby power system:
• The AC standby bus is powered from the batteries via the static inverter.
• The DC standby bus, battery bus, hot battery bus, and switched hot battery bus are powered directly from the battery/batteries.
Reference: FRM B737NG/MAX 6.2.6.2
Q.2.9 What does the STANDBY PWR OFF light indicate?
Illuminated (amber) – One or more of the following buses are unpowered:
• AC standby bus
• DC standby bus
• Battery bus
Reference: FRM B737NG/MAX 6.1.3
Q.2.10 With a LOSS OF BOTH ENGINE DRIVEN GENERATORS, what other source of electrical power may be available?
As the only power source, the APU generator can meet electrical power requirements for all ground conditions and most flight conditions.
Reference: FRM B737NG/MAX 6.2.2.2
Q.2.11 What considerations should you consider for starting the APU in flight following a LOSS OF BOTH ENGINE DRIVEN GENERATORS?
• APU start attempts are not recommended above 25,000 feet
• With both busses off, only one start attempt is recommended. Multiple start attempts reduce standby power capacity
Reference: B737NG QRH 6.5 / B737MAX QRH 6.6
Q.2.12 If the APU generator is the only remaining source of AC power, can you continue to your destination?
Only if the destination airport is the nearest suitable airport to you, as directed by the AOM and QRH.
Reference: AOM 5.1.1.2 / B737 QRH 6.4(MAX), 6.5 (NG)
Q.3.1 What fire detection/protection do the cargo compartments have?
• The forward and aft cargo compartments each have smoke detectors in a dual loop configuration. Normally, both detection loops must sense smoke to cause an alert.
• ETOPS aircraft have a total fire suppression time of 195 minutes. This includes 180 minutes to land at an airport plus an additional 15 minutes.
• Non-ETOPS aircraft provide for a 60-minute diversion and a 15-minute reserve totaling 75 minutes of fire suppression.
Reference: FRM B737NG/MAX 8.2.5.1 and 8.2.5.3
Q.3.2 Within how many minutes must you land after initial discharge of the cargo bay fire suppression system?
60 Minutes
(MAX8E/ -800E) – 180 Minutes
Note: E indicates ETOPS equipped aircraft.
Reference: AOM 3.15.1
Q.3.3 During a Cargo Fire Test, the Detector Fault light will illuminate under what condition?
If one or more detectors in the loop has failed.
Reference: FRM B737NG/MAX 8.2.8.1
Q.3.4 With a cargo fire, what indications would you expect to see after discharging the bottle?
After the initial indication of a cargo compartment fire and discharging the bottle, the FWD/AFT cargo fire warning light(s) can extinguish, remain illuminated, or re-illuminate over the remainder of the flight.
Reference: AOM 16.8.2
Q.3.5 During cruise, the Cargo Fire (FWD/ AFT) Warning light illuminates Red, Master Fire Warn lights illuminate and the fire warning bell sounds. What condition exists?
• At least one detector in each loop detects smoke
• With power failed in one loop, at least one detector on the remaining loop detects smoke
Reference: FRM B737NG/MAX 8.1.5
Q.3.7 On the ground during engine start and after the pushback Crew has been cleared off, they give you hand signals for an Engine Fire with no fire indications on the flight deck. What may be the actual condition?
You may have an Engine Tailpipe Fire.
Reference: QRH NG/MAX 8.14, AOM 5.7, FOM 18.4
Q.3.8 What occurs if one of the two engine fire detection loops fail with the OVHT DET switch in NORMAL?
If one loop fails with the OVHT DET switch in NORMAL, that loop is automatically deselected and the remaining loop functions as a single loop detector. There is no flight deck indication of single loop failure.
Reference: FRM B737NG/MAX 8.2.2.1
Q.3.9 What powers the engine overheat and fire detection? Extinguishing?
• Engine overheat and fire detection powered by the battery bus.
• Engine fire extinguishing powered by the hot battery bus.
Reference: FRM B737NG/MAX 8.2.2
Q.3.10 When selecting OVHT/FIRE during the Fire/Overheat Warning Test, you notice the FAULT Light is illuminated. What may be the problem and how do you determine in which engine the fault occurred?
If the FAULT light illuminates, a detection loop is inoperative. The related ENGINE FIRE WARNING switch and ENG OVERHEAT light do not illuminate.
Reference: AOM 16.8.1
Q.3.11 During a Cargo Fire Detection System Test, how can you determine if a loop is inoperative?
If a cargo fire warning light does not illuminate and the DETECTOR FAULT light does illuminate, a detection loop is inoperative.
Reference: AOM 16.8.2